This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents.

Rules and Regulations Federal Register

83813 

Vol. 88, No. 230 

Friday, December 1, 2023 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–1409; Project 

Identifier MCAI–2022–01645–T; Amendment 

39–22610; AD 2023–23–08] 

RIN 2120–AA64 

Airworthiness Directives; Airbus SAS 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding 

Airworthiness Directive (AD) 2019–07– 

05, which applied to all Airbus SAS 

Model A318 series airplanes; Model 

A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–211, –212, –214, –216, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. AD 

2019–07–05 required repetitive 

inspections for cracking of the 10VU 

rack fitting lugs and repair of any 

cracking. This AD continues to require 

the requirements of AD 2019–07–05, 

with reduced compliance times and 

removes airplanes having a certain 

modification from the applicability. 

This AD was prompted by a 

determination that certain repetitive 

inspection intervals need to be revised. 

The FAA is issuing this AD to address 

the unsafe condition on these products. 

DATES: This AD is effective January 5, 

2024. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of January 5, 2024. 

ADDRESSES: 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–1409; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this final rule, the mandatory 

continuing airworthiness information 

(MCAI), any comments received, and 

other information. The address for 

Docket Operations is U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

Material Incorporated by Reference: 

• For service information identified 

in this final rule, contact Airbus SAS, 

Airworthiness Office—EIAS, RondPoint Emile Dewoitine No: 2, 31700 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

website airbus.com. 

• You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available at 

regulations.gov under Docket No. FAA– 

2023–1409. 

FOR FURTHER INFORMATION CONTACT: 

Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; 

telephone 206–231–3667; email 

Timothy.P.Dowling@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2019–07–05, 

Amendment 39–19616 (84 FR 16386, 

April 19, 2019; corrected May 10, 2019 

(84 FR 20542)) (AD 2019–07–05). AD 

2019–07–05 applied to all Airbus SAS 

Model A318 series airplanes; Model 

A319–111, –112, –113, –114, –115, 

–131, –132, and –133 airplanes; Model 

A320–211, –212, –214, –216, –231, 

–232, and –233 airplanes; and Model 

A321–111, –112, –131, –211, –212, 

–213, –231, and –232 airplanes. AD 

2019–07–05 required repetitive 

inspections for cracking of the 10VU 

rack fitting lugs, and repair of any 

cracking. The FAA issued AD 2019–07– 

05 to address reading difficulties of 

flight-critical information displayed to 

the flightcrew during a critical phase of 

flight, such as an approach or takeoff, 

which could result in loss of airplane 

control at an altitude insufficient for 

recovery. 

The NPRM published in the Federal 

Register on July 13, 2023 (88 FR 44740). 

The NPRM was prompted by AD 2022– 

0266, dated December 22, 2022, issued 

by the European Union Aviation Safety 

Agency (EASA), which is the Technical 

Agent for the Member States of the 

European Union (EASA AD 2022–0266) 

(also referred to as the MCAI). The 

MCAI states that during an unscheduled 

maintenance operation on an A330 

airplane, the 10VU rack was removed 

for access, and cracks were discovered 

on 10VU rack side fittings on lugs 1, 3, 

and 4. As a similar design is installed 

on A320 family airplanes, a sampling 

review was done to determine the 

possible fleet impact. The result showed 

that several airplanes had cracked or 

broken 10VU rack side fittings. This 

condition, if not detected and corrected, 

could lead to a high vibration level on 

the primary flight and navigation 

displays during critical flight phases 

(take-off and landing), possibly creating 

reading difficulties for the crew. 

In the NPRM, the FAA proposed to 

continue to require repetitive 

inspections for cracking of the 10VU 

rack fitting lugs, and repair of any 

cracking. In the NPRM, the FAA also 

proposed to require reduced compliance 

times and to remove airplanes having a 

certain modification from the 

applicability. The FAA is issuing this 

AD to address reading difficulties of 

flight-critical information displayed to 

the flightcrew during a critical phase of 

flight, such as an approach or takeoff, 

which could result in loss of airplane 

control at an altitude insufficient for 

recovery. 

You may examine the MCAI in the 

AD docket at regulations.gov under 

Docket No. FAA–2023–1409. 

Discussion of Final Airworthiness 

Directive 

Comments 

The FAA received comments from Air 

Line Pilots Association, International 

(ALPA), who supported the NPRM 

without change. 

The FAA received additional 

comments from United Airlines 

(United). The following presents 

United’s comments received on the 

NPRM and the FAA’s response to each 

comment. 


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83814 Federal Register / Vol. 88, No. 230 / Friday, December 1, 2023 / Rules and Regulations 

Request To Revise Compliance Time 

United requested revising the 

proposed AD to add a grace period for 

the reduced compliance times of the 

repetitive inspections. United stated 

that it accomplished the initial 

inspections on most of the fleet and 

already scheduled the repetitive 

inspections within the 20,000-flightcycle or 40,000-flight-hour interval 

specified in AD 2019–07–05. United 

pointed out that the repetitive interval 

is reduced to 10,000 flight cycles or 

20,000 flight hours in the proposed AD. 

United suggested a grace period of 

20,000 flight cycles or 40,000 flight 

hours for the first repeat inspection and 

then 10,000 flight cycles or 20,000 flight 

hours for the following repeat 

inspections. 

The FAA does not agree with the 

commenter’s request to provide a grace 

period. In developing an appropriate 

compliance time for this action, the 

FAA considered the recommendations 

of the manufacturer and EASA, the 

urgency associated with the subject 

unsafe condition, the availability of 

required parts, and the practical aspect 

of accomplishing the required repair 

within a period of time that corresponds 

to the normal scheduled maintenance 

for most affected operators. The 

compliance times are not expected to 

ground any airplanes upon the effective 

date of this AD. United has not provided 

data for the FAA to consider. However, 

under the provisions of paragraph (l)(1) 

of this AD, the FAA will consider 

requests for approval of an extension of 

the compliance time if sufficient data 

are submitted to substantiate that the 

new compliance time would provide an 

acceptable level of safety. The FAA has 

not changed this AD in this regard. 

Request To Allow Flight With Known 

Cracking 

United requested that the FAA revise 

the proposed AD to align more closely 

with EASA AD 2022–0266; Airbus 

Service Bulletin A320–92–1087, 

Revision 04, dated May 16, 2022; and 

Airbus Service Bulletin A320–92–1119, 

Revision 02, dated May 16, 2022. United 

stated that these documents allow 

further flights up to 5,000 flight cycles, 

10,000 flight hours, or 24 months, 

whichever occurs first, after any finding 

of cracking on a single 10VU lug. The 

proposed AD would require repair 

before further flight for any number of 

lugs found to have cracking. 

The FAA generally does not allow 

flights with known cracking. Therefore, 

the FAA requires repairing known 

cracks before further flight (although the 

FAA might make exceptions in certain 

cases of unusual need, as discussed 

below). This is based on the fact that 

such damaged airplanes do not conform 

to the FAA-certificated type design and, 

therefore, are not airworthy until a 

properly approved repair is made. 

While the FAA recognizes that repair 

deferrals might be necessary at times, 

the FAA intends to minimize adverse 

human factors relating to the lack of 

reliability of long-term repetitive 

inspections, which might reduce the 

safety of the type-certificated design if 

such repair deferrals are practiced 

routinely. 

As noted above, the FAA might allow 

an exception to these requirements in 

certain cases, if there is an unusual need 

for a temporary deferral and if the 

temporary fix will maintain an adequate 

level of safety. Unusual needs include 

such circumstances as legitimate 

difficulty in acquiring parts to 

accomplish repairs. Under such 

conditions, the FAA might allow a 

temporary deferral of the repair, subject 

to a stringent inspection program 

acceptable to the FAA. The FAA 

acknowledges that the manufacturer has 

specified inspection intervals that are 

intended to allow continued operation 

with known cracks, and to prevent the 

need for extensive repairs. However, 

since the FAA is not aware of any 

unusual need for repair deferral in 

regard to this AD, the FAA has not 

evaluated these inspection intervals. 

The FAA considers the compliance 

times in this AD to be adequate to allow 

operators to acquire parts to have on 

hand in the event that a crack is 

detected during inspection. Therefore, 

the FAA has determined that, due to the 

safety implications and consequences 

associated with such cracking, any 

10VU lug that is found to be cracked 

must be repaired or modified before 

further flight. The FAA has not changed 

this AD in this regard. 

Conclusion 

This product has been approved by 

the aviation authority of another 

country and is approved for operation in 

the United States. Pursuant to the FAA’s 

bilateral agreement with this State of 

Design Authority, it has notified the 

FAA of the unsafe condition described 

in the MCAI referenced above. The FAA 

reviewed the relevant data, considered 

the comments received, and determined 

that air safety requires adopting this AD 

as proposed. Accordingly, the FAA is 

issuing this AD to address the unsafe 

condition on this product. Except for 

minor editorial changes, this AD is 

adopted as proposed in the NPRM. 

None of the changes will increase the 

economic burden on any operator. 

Related Service Information Under 1 

CFR Part 51 

The FAA reviewed Airbus Service 

Bulletins A320–92–1087, Revision 04, 

dated May 16, 2022; and A320–92– 

1119, Revision 02, dated May 16, 2022. 

This service information specifies 

procedures for repetitive inspections for 

cracking of the 10VU rack fitting lugs, 

and repair of any cracking. These 

documents are distinct since they apply 

to different airplane configurations. This 

service information is reasonably 

available because the interested parties 

have access to it through their normal 

course of business or by the means 

identified in the ADDRESSES section. 

Costs of Compliance 

The FAA estimates that this AD 

affects 461 airplanes of U.S. registry. 

The FAA estimates the following 

costs to comply with this AD: 

ESTIMATED COSTS FOR REQUIRED ACTIONS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Inspections (retained actions from AD 2019– 

07–05).

2 work-hours × $85 per hour = $170 ............. $0 $170 $78,370 

The FAA estimates that it would take 

about 1 work-hour per product to 

comply with the reporting requirement 

in this AD. The average labor rate is $85 

per hour. Based on these figures, the 

FAA estimates the cost of reporting the 

inspection results on U.S. operators to 

be $85 per product. 

The FAA estimates the following 

costs to do any necessary repairs that 

would be required based on the results 

of the inspection. The FAA has no way 

of determining the number of aircraft 

that might need these repairs: 


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Federal Register / Vol. 88, No. 230 / Friday, December 1, 2023 / Rules and Regulations 83815 

ESTIMATED COSTS OF ON-CONDITION ACTIONS

Labor cost Parts cost Cost per 

product 

83 work-hours × $85 per hour = $7,055 ................................................................................................................. $9,140 $16,195 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to a penalty for failure to comply with 

a collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a currently valid 

OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public 

reporting for this collection of 

information is estimated to take 

approximately 1 hour per response, 

including the time for reviewing 

instructions, searching existing data 

sources, gathering and maintaining the 

data needed, and completing and 

reviewing the collection of information. 

All responses to this collection of 

information are mandatory. Send 

comments regarding this burden 

estimate or any other aspect of this 

collection of information, including 

suggestions for reducing this burden, to: 

Information Collection Clearance 

Officer, Federal Aviation 

Administration, 10101 Hillwood 

Parkway, Fort Worth, TX 76177–1524. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

The FAA is issuing this rulemaking 

under the authority described in 

Subtitle VII, Part A, Subpart III, Section 

44701: General requirements. Under 

that section, Congress charges the FAA 

with promoting safe flight of civil 

aircraft in air commerce by prescribing 

regulations for practices, methods, and 

procedures the Administrator finds 

necessary for safety in air commerce. 

This regulation is within the scope of 

that authority because it addresses an 

unsafe condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

The FAA determined that this AD 

will not have federalism implications 

under Executive Order 13132. This AD 

will not have a substantial direct effect 

on the States, on the relationship 

between the national government and 

the States, or on the distribution of 

power and responsibilities among the 

various levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Will not affect intrastate aviation 

in Alaska, and 

(3) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by: 

■ a. Removing Airworthiness Directive 

(AD) 2019–07–05, Amendment 39– 

19616 (84 FR 16386, April 19, 2019; 

corrected May 10, 2019 (84 FR 20542)); 

and 

■ b. Adding the following new AD: 

2023–23–08 Airbus SAS: Amendment 39– 

22610; Docket No. FAA–2023–1409; 

Project Identifier MCAI–2022–01645–T. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective January 5, 2024. 

(b) Affected ADs 

This AD replaces AD 2019–07–05, 

Amendment 39–19616 (84 FR 16386, April 

19, 2019; corrected May 10, 2019 (84 FR 

20542)) (AD 2019–07–05). 

(c) Applicability 

This AD applies to the Airbus SAS 

airplanes identified in paragraphs (c)(1) 

through (4) of this AD, certificated in any 

category, all manufacturer serial numbers, 

except those on which Airbus modification 

157335 has been embodied in production. 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –216, 

–231, –232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 92, Electric and electronic 

common installation. 

(e) Unsafe Condition 

This AD was prompted by a report of 

cracks found during maintenance inspections 

on certain 10VU rack fitting lugs, and a 

determination that certain compliance times 

need to be revised. The FAA is issuing this 

AD to address reading difficulties of flightcritical information displayed to the 

flightcrew during a critical phase of flight, 

such as an approach or takeoff, which could 

result in loss of airplane control at an altitude 

insufficient for recovery. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Definitions, With No Changes 

This paragraph restates the definitions of 

paragraph (g) of AD 2019–07–05, with no 

changes. For the purpose of this AD, Group 

1 airplanes are in a pre-Airbus Modification 

35869 configuration, and Group 2 airplanes 

are in a post-Airbus Modification 35869 

configuration. 

(h) Retained Repetitive Inspections, With 

Reduced Inspection Intervals and Revised 

Service Information 

This paragraph restates the requirements of 

paragraph (h) of AD 2019–07–05, with 

reduced inspection intervals and revised 

service information. 

(1) For Group 1 airplanes: At the later of 

the times specified in Figure 1 to paragraph 

(h)(1) of this AD, do a detailed inspection for 

cracking of the 10VU rack fitting lugs, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

92–1087, Revision 04, dated May 16, 2022. 

Repeat the inspection thereafter at intervals 

not to exceed 10,000 flight cycles or 20,000 

flight hours, whichever occurs first. 

Figure 1 to Paragraph (h)(1)—Initial 

Inspection Compliance Time for Group 1 

Airplanes 


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(2) For Group 2 airplanes: At the later of 

the times specified in Figure 2 to paragraph 

(h)(2) of this AD, do a detailed inspection for 

cracking of the 10VU rack fitting lugs, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

92–1119, Revision 02, dated May 16, 2022. 

Repeat the inspection thereafter at intervals 

not to exceed 10,000 flight cycles or 20,000 

flight hours, whichever occurs first. 

Figure 2 to Paragraph (h)(2)—Initial 

Inspection Compliance Time for Group 2 

Airplanes 

(i) Retained Repair, With Revised Service 

Information 

This paragraph restates the requirements of 

paragraph (i) of AD 2019–07–05, with revised 

service information. If any crack is found 

during any inspection required by paragraph 

(h)(1) or (2) of this AD: Before further flight, 

do a repair in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–92–1087, Revision 04, 

dated May 16, 2022 (for Group 1 airplanes); 

or Airbus Service Bulletin A320–92–1119, 

Revision 02, dated May 16, 2022 (for Group 

2 airplanes); as applicable. Repair of a 10VU 

rack fitting lug does not terminate the 

repetitive inspections required by paragraphs 

(h)(1) and (2) of this AD. 

(j) Reporting Requirement 

At the applicable time specified in 

paragraph (j)(1) or (2) of this AD: Submit a 

report of findings (positive and negative) of 

each inspection required by paragraph (h) of 

this AD to Airbus Service Bulletin Reporting 

Online Application on Airbus World 

(airbus.com) or in accordance with B. 

‘‘Reporting Sheet’’ of the Appendix of Airbus 

Service Bulletin A320–92–1087, Revision 04, 

dated May 16, 2022 (for Group 1 airplanes); 

or Airbus Service Bulletin A320–92–1119, 

Revision 02, dated May 16, 2022 (for Group 

2 airplanes); as applicable. 

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (h)(1) and (i) 

of this AD, if those actions were performed 

before May 24, 2019 (the effective date of AD 

2019–07–05), using Airbus Service Bulletin 

A320–92–1087, dated March 28, 2011, which 

is not incorporated by reference in this AD; 

or Airbus Service Bulletin A320–92–1087, 

Revision 01, dated May 17, 2011, which is 

not incorporated by reference in this AD; or 

Airbus Service Bulletin A320–92–1087, 

Revision 02, dated November 25, 2014, 

which was incorporated by reference in AD 

2016–19–14. 

(2) This paragraph provides credit for 

actions required by paragraphs (h)(1) and (i) 

of this AD, if those actions were performed 

before the effective date of this AD, using 

Airbus Service Bulletin A320–92–1087, 

Revision 03, dated July 31, 2017, which was 

incorporated by reference in AD 2019–07–05. 

(3) This paragraph provides credit for 

actions required by paragraphs (h)(2) and (i) 

of this AD, if those actions were performed 

before the effective date of this AD, using 

Airbus Service Bulletin A320–92–1119, 

dated July 28, 2017, which was incorporated 

by reference in AD 2019–07–05; or Airbus 

Service Bulletin A320–92–1119, Revision 01, 

dated August 5, 2019, which is not 

incorporated by reference in this AD. 

(4) This paragraph provides credit for the 

reporting required by paragraph (j)(2) of this 

AD, if that action was performed before the 

effective date of this AD in accordance with 

the instructions of Airbus Service Bulletin 

A320A–92–1087, Revision 03, dated July 31, 

2017 (for Group 1 airplanes); or Airbus 

Service Bulletin A320–92–1119, dated July 

28, 2017 (for Group 2 airplanes); as 

applicable; except where Figure A–FAAAA, 

Sheet 02, of Appendix 01, ‘‘Inspection 

Report,’’ of Airbus Service Bulletin A320– 

92–1087, Revision 03, dated July 31, 2017; 

and Figure A–FAAAA, Sheet 02, of 

Appendix 01, ‘‘Inspection Report,’’ of Airbus 

Service Bulletin A320–92–1119, dated July 

28, 2017; specifies sending removed lugs to 

Airbus for investigation, that action is not 

required by this AD. Airbus Service Bulletin 


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Compliance Time (whichever occurs later, A or B) 

A Prior to exceeding 30,000 total flight cycles or 60,000 total 

flight hours, whichever occurs first; or within 24 months after 

November 22, 2016 (the effective date of AD 2016-19-14, 

Amendment 39-18663 (81 FR 71602, October 18, 2016)) (AD 

2016-19-14); whichever occurs later 

B Within 24 months after the effective date of this AD, without 

exceeding 20,000 flight cycles or 40,000 flight hours, 

whichever occurs first, since the most recent inspection done 

as specified in Airbus Service Bulletin A320-92-1087 

Compliance Time (whichever occurs later, A or B) 

A Prior to exceeding 30,000 total flight cycles or 60,000 total 

flight hours, whichever occurs first; or within 30 days after 

May 24, 2019 (the effective date of AD 2019-07-05); 

whichever occurs later. 

B Within 24 months after the effective date of this AD, without 

exceeding 20,000 flight cycles or 40,000 flight hours, 

whichever occurs first, since the most recent inspection done 

as specified in Airbus Service Bulletin A320-92-1119 
Federal Register / Vol. 88, No. 230 / Friday, December 1, 2023 / Rules and Regulations 83817 

A320A–92–1087, Revision 03, dated July 31, 

2017; and Airbus Service Bulletin A320–92– 

1119, dated July 28, 2017; were incorporated 

by reference in AD 2019–07–05. 

(l) Additional AD Provisions 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Validation Branch, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or 

responsible Flight Standards Office, as 

appropriate. If sending information directly 

to the manager of the International Validation 

Branch, mail it to the address identified in 

paragraph (m)(2) of this AD or email to: 9- 

AVS-AIR-730-AMOC@faa.gov. If mailing 

information, also submit information by 

email. 

(i) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the responsible Flight Standards Office. 

(ii) Global AMOC AIR–676–19–305, dated 

July 29, 2019, approved as an AMOC for AD 

2019–07–05, is approved as an AMOC for the 

corresponding provisions of this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain instructions 

from a manufacturer, the instructions must 

be accomplished using a method approved 

by the Manager, International Validation 

Branch, FAA; or the European Union 

Aviation Safety Agency (EASA); or Airbus 

SAS’s EASA Design Organization Approval 

(DOA). If approved by the DOA, the approval 

must include the DOA-authorized signature. 

(3) Required for Compliance (RC): Except 

as required by paragraph (l)(2) of this AD, if 

any service information contains procedures 

or tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 

as RC may be deviated from using accepted 

methods in accordance with the operator’s 

maintenance or inspection program without 

obtaining approval of an AMOC, provided 

the procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(m) Additional Information 

(1) Refer to European Union Aviation 

Safety Agency (EASA) AD 2022–0266, dated 

December 22, 2022, for related information. 

This EASA AD may be found in the AD 

docket at regulations.gov under Docket No. 

FAA–2023–1409. 

(2) For more information about this AD, 

contact Timothy Dowling, Aviation Safety 

Engineer, FAA, 1600 Stewart Avenue, Suite 

410, Westbury, NY 11590; phone 206–231– 

3667; email Timothy.P.Dowling@faa.gov. 

(3) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(3) and (4) of this AD. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Airbus Service Bulletin A320–92–1087, 

Revision 04, dated May 16, 2022. 

(ii) Airbus Service Bulletin A320–92–1119, 

Revision 02, dated May 16, 2022. 

(3) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EIAS, Rond-Point Emile Dewoitine 

No: 2, 31700 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; website airbus.com. 

(4) You may view this service information 

at the FAA, Airworthiness Products Section, 

Operational Safety Branch, 2200 South 216th 

St., Des Moines, WA. For information on the 

availability of this material at the FAA, call 

206–231–3195. 

(5) You may view this material at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, 

visit www.archives.gov/federal-register/cfr/ 

ibr-locations or email fr.inspection@nara.gov. 

Issued on November 16, 2023. 

Ross Landes, 

Deputy Director for Regulatory Operations, 

Compliance & Airworthiness Division, 

Aircraft Certification Service. 

[FR Doc. 2023–26404 Filed 11–30–23; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2023–2154; Project 

Identifier MCAI–2023–00763–T; Amendment 

39–22612; AD 2023–23–10] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

(Type Certificate Previously Held by 

Yabora ̃ Indu ́ stria Aerona ́utica S.A.; 

Embraer S.A.) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for all 

Embraer S.A. Model ERJ 190–300 

airplanes. This AD was prompted by a 

report of unexpected wear on the wing 

hinge bearing assembly of the aileron 

surfaces found during the functional test 

of the aileron control system backlash. 

This AD requires repetitive inspections 

of the press-fitted bushings of the wing 

ailerons for migration and broken 

sealant, measurements of the distance 

between the aileron surfaces and hinge 

fittings, functional checks of the 

backlash of the wing aileron control 

system, and all applicable related 

investigative and corrective actions, as 

specified in an Ageˆncia Nacional de 

Aviac ̧a ̃o Civil (ANAC) AD, which is 

incorporated by reference. The FAA is 

issuing this AD to address the unsafe 

condition on these products. 

DATES: This AD is effective December 

18, 2023. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 18, 2023. 

The FAA must receive comments on 

this AD by January 16, 2024. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

regulations.gov. Follow the instructions 

for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE, 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

AD Docket: You may examine the AD 

docket at regulations.gov under Docket 

No. FAA–2023–2154; or in person at 

Docket Operations between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this final rule, the mandatory 

continuing airworthiness information 

(MCAI), any comments received, and 

other information. The street address for 

Docket Operations is listed above. 

Material Incorporated by Reference: 

• For material incorporated by 

reference in this AD, contact National 

Civil Aviation Agency (ANAC), 

Aeronautical Products Certification 

Branch (GGCP), Rua Dr. Orlando 

Feirabend Filho, 230—Centro 

Empresarial Aquarius—Torre B— 

Andares 14 a 18, Parque Residencial 

Aquarius, CEP 12.246–190—Sa ̃o Jose ́

dos Campos—SP, Brazil; telephone 55 

(12) 3203–6600; email pac@anac.gov.br; 

website anac.gov.br/en/. You may find 

this material on the ANAC website at 

sistemas.anac.gov.br/certificacao/DA/ 

DAE.asp. 

• You may view this service 

information at the FAA, Airworthiness 

Products Section, Operational Safety 

Branch, 2200 South 216th St., Des 

Moines, WA. For information on the 

availability of this material at the FAA, 

call 206–231–3195. It is also available at 


lotter on DSK11XQN23PROD with RULES1